A launch stand system for liquid rocket assisted support and its working method

Abstract

The application provides a vertical rack system for liquid rocket auxiliary support and a working method thereof, which comprises a vertical rack main structure, an upper clamp, a lower clamp, a main support bracket, an auxiliary support bracket, a spring limiting tool and a screw elevator structure; the upper clamp and the lower clamp are fixedly connected on the vertical rack main structure at intervals; the main support bracket and the auxiliary support bracket are arranged on the vertical rack main structure at intervals; and the auxiliary support bracket is connected on the vertical rack main structure through the spring limiting tool and the screw elevator structure. The application improves the support stability, reliability and safety of the vertical rack main structure on the rocket during the transfer, erection and launching process of the rocket, improves the reliability, efficiency, precision and safety of the docking of the vertical rack and the launching platform, and realizes the fast, safe and high-precision transfer, erection and launching docking process.

Description

Technical Field

[0001] This application relates to the field of rocket transport and erection technology, and in particular to an erection frame system for auxiliary support of liquid rockets and its working method. Background Technology

[0002] Currently, ensuring the safety and stability of rockets during transport and erection is of paramount importance. Existing rocket transport support systems mostly employ mechanical structures, but these suffer from problems such as insufficient support force and difficulties in adjustment.

[0003] The existing patent publication number, CN111023899B, discloses a rocket transport and erection system, which includes an erection arm, a self-propelled hydraulic axle vehicle, and a launch pad. The erection arm is mounted on the self-propelled hydraulic axle vehicle, and the supported rocket is positioned on top of the erection arm along its length. The self-propelled hydraulic axle vehicle is used to transport the supported rocket to the launch pad via the erection arm. Along the length of the erection arm, a rocket support clamping device, a rocket auxiliary hydraulic support device, and a rocket rear pivot support adjustment device are sequentially arranged on the erection arm. The rocket support clamping device, the rocket auxiliary hydraulic support device, and the rocket rear pivot support adjustment device constitute a three-point support for the rocket. However, this rocket transport and erection system cannot erect heavy (500t-1000t class) liquid rockets, has low reliability and poor stability in supporting the rocket, and the insufficient support force of the erection frame easily leads to deformation, making it impossible to safely, accurately, and quickly erect heavy rockets.

[0004] Therefore, the urgent technical problem to be solved is that the existing rockets have insufficient support, large deformation, and difficulty in docking and adjustment during transportation and erection, which leads to the risk of instability, collisions, or even structural damage to the rocket body. Summary of the Invention

[0005] The purpose of this application is to provide an erection frame system for auxiliary support of liquid rockets and its working method, which improves the stability, reliability and safety of the main structure of the erection frame in supporting the rocket during the rocket transport, erection and launch process, as well as improves the reliability, efficiency, accuracy and safety of the docking between the erection frame and the launch pad, and realizes a fast, safe and high-precision transport, erection and launch docking process.

[0006] To achieve the above objectives, as a first aspect of this application, this application provides an erection frame system for auxiliary support of liquid rockets. The system includes: an erection frame main structure, an upper clamp, a lower clamp, a main support bracket, an auxiliary support bracket, a spring-limiting fixture, and a screw-lift mechanism. The upper clamp and the lower clamp are fixedly connected to the erection frame main structure at a distance from each other. The main support bracket and the auxiliary support bracket are disposed at a distance from each other on the erection frame main structure. The auxiliary support bracket is connected to the erection frame main structure via the spring-limiting fixture and the screw-lift mechanism.

[0007] The erecting frame system for auxiliary support of liquid rockets as described above includes an auxiliary rocket support base and a guide column structure; the guide column structure is disposed at the bottom of the auxiliary rocket support base.

[0008] The erecting frame system for auxiliary support of liquid rockets as described above includes a spring-limiting fixture and a screw jack structure comprising: a jack base, a spring-compressing limiting structure, a screw jack, and a servo motor; the jack base is fixedly connected to the main structure of the erecting frame; the screw jack is fixedly connected to the jack base; one end of the spring-compressing limiting structure is fixedly connected to the screw jack, and the other end is connected to the rocket support via a spherical bearing; the screw jack is connected to the servo motor; a pressure sensor is also provided between the spherical bearing and the spring-compressing limiting structure.

[0009] The erector system for auxiliary support of liquid rockets as described above, wherein the guide column structure includes: a guide column and a guide seat; the guide seat is fixedly connected to the main structure of the erector; and the guide column is vertically movably connected within the guide seat.

[0010] The erecting frame system for auxiliary support of liquid rockets as described above, wherein the upper clamp includes: an upper clamp base, a hinge support, a first upper clamp holding frame, a second upper clamp holding frame, a first push screw, a second push screw, and an upper clamp holding plate; the upper clamp base and the hinge support are fixedly connected to the main structure of the erecting frame; one end of the bottom of the first upper clamp holding frame is connected to the hinge support via a pivot; the other end is connected to the upper clamp base via the first push screw; one end of the first push screw is connected to the upper clamp base... The clamp base is rotatably connected, and the other end is rotatably connected to the first upper clamp holding frame; one top end of the first upper clamp holding frame is rotatably connected to the bottom of the second upper clamp holding frame, and the other end is connected to the second push screw; the top of the second upper clamp holding frame is connected to the second push screw; the upper clamp holding plate is connected to the top of the second upper clamp holding frame; the first push screw extends and retracts to drive the first upper clamp holding frame to open and close; the second push screw extends and retracts to drive the second upper clamp holding frame to open and close.

[0011] The erecting frame system for auxiliary support of liquid rockets as described above, wherein the main support bracket includes: a main rocket support bracket, a rocket support bracket base, and a connecting erecting frame base; the main rocket support bracket is fixedly connected to the rocket support bracket base; the main rocket support bracket has an arc-shaped groove for supporting the rocket body; the rocket support bracket base is fixedly connected to the connecting erecting frame base; and the connecting erecting frame base is fixedly connected to the main erecting frame structure.

[0012] The erector system for auxiliary support of liquid rockets as described above, wherein the auxiliary rocket support has an arc-shaped groove for supporting the rocket body; the inner wall of the arc-shaped groove is provided with felt.

[0013] The erecting frame system for auxiliary support of liquid rockets as described above, wherein the spring compression limiting structure includes: an outer cylinder, a spring, and a movable column; the spring is disposed inside the outer cylinder; the movable column is movably connected inside the outer cylinder, the bottom end of the movable column abuts against the spring, and the top end of the movable column is connected to the auxiliary support bracket through a pressure sensor and a joint bearing.

[0014] As described above, the erecting frame system for auxiliary support of liquid rockets includes two guide column structures, both of which are located at the bottom of the auxiliary rocket support and are respectively located on both sides of the spring limiting fixture and the screw lift structure.

[0015] As a second aspect of this application, this application provides a method for operating an erection frame system for auxiliary support of a liquid rocket. The method includes: upper clamps and lower clamps fixing and holding the rocket; main support brackets and auxiliary support brackets jointly supporting the rocket body and completing longitudinal adjustment; the auxiliary support bracket automatically rising, contacting and pressing the rocket body; the rocket being transferred to the launch pad, the main structure of the erection frame docking with the launch pad, and the rocket body being erected.

[0016] The beneficial effects achieved by this application are as follows: (1) This application adopts a three-point layout of main support bracket and two auxiliary support brackets, and iteratively optimizes the main structure of the erecting frame with zero support as the control condition to reduce the maximum deflection of the rocket body during transportation, eliminate the additional deformation caused by insufficient rigidity of the front end of the frame, and avoid the limited support force and deformation of the main structure of the erecting frame.

[0017] (2) The upper support point of the erecting cylinder in this application is connected to the erecting cylinder through an automatic connecting pin mechanism. An automatic connecting pin mechanism is also provided at the connection between the main structure of the erecting frame and the slewing shaft lug plate, which ensures that the main structure of the erecting frame and the launch pad can be quickly and accurately docked during the docking process.

[0018] (3) The main body of the erecting frame of this application is a truss structure, which integrates air conditioning pipes, venting connectors, plug-in supports, video surveillance, personnel passages, etc., thereby improving the integration of equipment and reducing additional supports. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0020] Figure 1 This is a schematic diagram of the structure of an erection frame system for auxiliary support of a liquid rocket, according to an embodiment of this application.

[0021] Figure 2 This is a top view of an erection frame system for auxiliary support of a liquid rocket, according to an embodiment of this application.

[0022] Figure 3 This is a schematic diagram of the structure of the upper clamp holding the arrow body according to an embodiment of this application.

[0023] Figure 4 This is a schematic diagram of the upper clamp being opened according to an embodiment of this application.

[0024] Figure 5 This is a schematic diagram showing the connection between the spring limiting fixture and the screw jack structure and the auxiliary support bracket in an embodiment of this application.

[0025] Figure 6 This is a schematic diagram of the structure of the spring limiting fixture and the screw jack in an embodiment of this application.

[0026] Figure 7 This is a schematic diagram of the guide column structure according to an embodiment of this application.

[0027] Figure 8 This is a schematic diagram of the main support bracket in an embodiment of this application.

[0028] Figure 9 This is a schematic diagram of the erection frame system structure according to an embodiment of this application.

[0029] Figure reference numerals: 1-Erecting frame main structure; 2-Upper clamp; 3-Lower clamp; 4-Auxiliary support bracket; 5-Spring limit fixture and screw jack structure; 6-Main support bracket; 11-Secondary disengagement and recovery device; 12-Operating platform; 13-Gas supply and distribution pipeline; 14-Air conditioning and ventilation pipeline; 15-Elevator car; 16-Electrical distribution box; 21-Upper clamp base; 22-Hinge support; 23-First push screw; 24-First upper clamp Clamping frame; 25-Second push screw; 26-Second upper clamp clamping frame; 27-Upper clamp arrow holding plate; 41-Auxiliary arrow support; 42-Guide column structure; 51-Elevator base; 52-Spring compression limit structure; 53-Screw elevator; 54-Servo motor; 55-Joint bearing; 56-Pressure sensor; 61-Main arrow support; 62-Arrow support base; 63-Connecting erecting frame base; 421-Guide seat; 422-Guide column. Detailed Implementation

[0030] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0031] like Figure 1 , 2 As shown in Figure 9, this application provides an erection frame system for auxiliary support of liquid rockets. The system includes: an erection frame main structure 1, an upper clamp 2, a lower clamp 3, a main support bracket 6, an auxiliary support bracket 4, and a spring-limiting fixture and a screw jack structure 5; the upper clamp 2 and the lower clamp 3 are fixedly connected to the erection frame main structure 1 at intervals; the main support bracket 6 and the auxiliary support bracket 4 are disposed at intervals on the erection frame main structure 1; the auxiliary support bracket 4 is connected to the erection frame main structure 1 through the spring-limiting fixture and the screw jack structure 5.

[0032] As a specific embodiment of the present invention, the erector system horizontally supports the rocket body during the entire rocket transfer process, locking and protecting the rocket body; after docking with the launch pad at the launch site, the rocket body is erected, changing the rocket body from a horizontal state to a vertical launch state. The upper clamp 2 is used to fix the rocket in both horizontal and vertical directions during transportation, ensuring the safety of the rocket body during transfer, and fixing and protecting the rocket body during the erection to the vertical launch state. The main support bracket 6 is connected to the rocket support base 62 by bolts. The rocket support base 62 is welded to the base, and the base is welded to the main structure 1 of the erector, allowing for longitudinal adjustment. The auxiliary support bracket 4 is used to assist in supporting the rocket body, using a spring and screw lift adjustment method, which can achieve manual and automatic control. The lower clamp 3 is used to support the tail end journal of the rocket during horizontal transfer, and locks the journal before erection to prevent the rocket body from sliding backward or rotating; it is released after erection.

[0033] As a specific embodiment of the present invention, the main structure 1 of the erecting frame is used to provide support for the pipelines and cables of the filling and gas supply system; it is equipped with air conditioning ventilation pipelines to ensure the temperature, humidity and cleanliness inside the fairing; it provides installation support for the secondary disconnect cable and the primary disconnect cable of the avionics system; it provides structural, pipeline and cable support for the fairing air conditioning connector, liquid oxygen / kerosene filling and draining connector and gas pipe connector detachment and recovery protection device; and it provides access and platform for personnel after erection.

[0034] In a specific embodiment of the present invention, the end of the erecting frame main structure 1 is rotatably connected to the fixed launch platform via a rotary shaft lug and a rotary shaft. The rotary shaft lug is fixedly connected to the fixed launch platform, and the rotary shaft connects the end of the erecting frame main structure 1 to the rotary shaft lug.

[0035] As a specific embodiment of the present invention, the bottom of the main body structure 1 of the erecting frame is provided with an upper support point for the erecting cylinder, which is connected to the erecting cylinder through an automatic connecting pin mechanism. An automatic connecting pin mechanism is also provided at the connection between the main body structure 1 of the erecting frame and the slewing shaft lug plate, so as to ensure that the main body structure 1 of the erecting frame and the launch pad can achieve fast and accurate docking during the docking process.

[0036] As a specific embodiment of the present invention, a video monitoring system (excluding camera-related hardware) is installed on the main structure 1 of the erecting frame, which can monitor the status of the kerosene filling and draining connector, liquid oxygen filling and draining connector, gas pipe connector, secondary disconnecting connector, and rectifier air conditioning connector.

[0037] like Figure 9As shown, the main structure 1 of the launch erector is a truss structure. The main structure 1 is equipped with a two-stage disengagement and recovery device 11, an operating platform 12, a fueling and gas supply pipeline 13, an air conditioning and ventilation pipeline 14, an elevator car 15, and a power distribution box 16. This invention integrates multiple functions onto the main structure 1 of the launch erector, upgrading the launch erector from a simple rocket body flipping fixture to a platform for the rocket ground support system. It achieves integration of structure, piping, electrical systems, environment, and operation, resulting in faster, lighter, and safer launch preparation.

[0038] As a specific embodiment of the present invention, a finite element simulation algorithm is used to calculate the deformation of the main structure 1 of the erecting frame, and the simulation results encompass the actual working conditions. After multiple rounds of iterative calculations, it is identified that the stiffness of the front end of the frame is relatively weak, resulting in limited support force for the erecting frame. Therefore, an auxiliary support bracket 4 is set to avoid the limited support force and deformation of the main structure 1 of the erecting frame.

[0039] like Figure 5 As shown, the auxiliary support bracket 4 includes an auxiliary arrow support 41 and a guide column structure 42; the guide column structure 42 is located at the bottom of the auxiliary arrow support 41. The auxiliary support bracket 4 adopts a spring-loaded screw jack adjustment mechanism. The screw jack 53 is equipped with a handwheel and an electric drive system and a soft starter. The lifting and lowering adjustment of the auxiliary support bracket 4 can be controlled manually or automatically by the starter.

[0040] In a preferred embodiment of the present invention, the auxiliary arrow support 41 and the guide column structure 42 are connected by bolts, allowing for an adjustment range of ±25mm in the X direction. The auxiliary support support 4 is connected to the main structure 1 of the erecting frame by bolts, with a reserved adjustment range of ±5mm in the Y direction to accommodate manufacturing errors.

[0041] like Figure 5 and 6 As shown, the spring-limiting fixture and screw jack structure 5 includes: a jack base 51, a spring-pressing limiting structure 52, a screw jack 53, and a servo motor 54; the jack base 51 is fixedly connected to the main structure 1 of the erecting frame; the screw jack 53 is fixedly connected to the jack base 51; one end of the spring-pressing limiting structure 52 is fixedly connected to the screw jack 53, and the other end is connected to the arrow support via a spherical bearing 55; the screw jack 53 is connected to the servo motor 54; a pressure sensor 56 is also provided between the spherical bearing 55 and the spring-pressing limiting structure 52.

[0042] In a preferred embodiment of the present invention, the screw stroke of the screw jack 53 of the auxiliary support bracket 4 is 100mm. During the hoisting and transfer docking of the entire rocket, the front end of the rocket body contacts the main support bracket 6 via hoisting, and the rear end journal rests on the lower clamp 3. After adjusting the rocket body posture, the lower clamp 3 locks the end journal. At this time, the two auxiliary support brackets 4 need to be adjusted to the designated position to support the rocket body. The two auxiliary support brackets 4 are raised by automatic electric control. After the two auxiliary support brackets 4 contact the rocket body, they need to continue to rise to press the rocket body. The torque is monitored by the servo motor 54, and the pressure data is used as the upper limit for monitoring by the pressure sensor 56. During the erection process, when the auxiliary support brackets 4 need to be lowered, the PLC simultaneously outputs a signal to the DO module. The DO signal is sent to the soft starter to control the servo motor 54 to run simultaneously, completing the simultaneous descent of each auxiliary support bracket 4. During the entire erection process and after the erection is completed, the main support bracket 6 and the auxiliary support brackets 4 do not contact the rocket body.

[0043] like Figure 7 As shown, the guide column structure 42 includes a guide column 422 and a guide seat 421; the guide seat 421 is fixedly connected to the main structure 1 of the erecting frame; the guide column 422 is vertically and movably connected within the guide seat 421. Preferably, a mechanical upper limit mechanism is provided on the guide seat 421. The mechanical upper limit mechanism limits the maximum upward stroke of the guide column 422.

[0044] As a specific embodiment of the present invention, the screw jack 53 is a worm gear screw jack, which includes a worm gear and an auxiliary support screw. The servo motor 54 is an explosion-proof servo motor. The auxiliary support screw is meshed with the worm gear and is arranged in a vertical direction. The worm gear is connected to the explosion-proof servo motor, which drives the worm gear to rotate. The rotation of the worm gear drives the auxiliary support screw to rise and fall.

[0045] Preferably, a pressure sensor 56 is installed at the bottom of each auxiliary support bracket 4, and two retraction proximity switches are installed on the auxiliary support lead screw. The pressure sensor 56 at the bottom of the auxiliary support bracket 4 is used to measure the force exerted on the support rocket body. The pressure sensor 56 provides a 4~20mA current, which is connected to the isolation barrier inside the control cabinet through the explosion-proof junction box of the auxiliary support, splitting the AI ​​signal into two paths, which are then connected to different AI modules. Subsequently, the AI ​​signal is sent by the baseboard bus module to the EST-200M interface module, and then sent to the controller via the PROFINET IO protocol for processing and conversion into support force data.

[0046] The control system controls the extension and retraction of the auxiliary support screw based on the data from the shaft angle encoder on the servo motor 54. Data from the pressure sensor 56 is used to cut off the auxiliary support screw's movement in an emergency. In case of pressure sensor 56 failure, the auxiliary support screw's movement is stopped by the servo motor torque and mechanical limit switches. A retraction proximity switch on the auxiliary support screw protects it from damage.

[0047] like Figure 3 and 4 As shown, the upper clamp 2 includes: an upper clamp base 21, a hinge support 22, a first upper clamp holding frame 24, a second upper clamp holding frame 26, a first push screw 23, a second push screw 25, and an upper clamp arrow-holding pressure plate 27; the upper clamp base 21 and the hinge support 22 are fixedly connected to the main structure 1 of the erecting frame by bolts; one end of the bottom of the first upper clamp holding frame 24 is connected to the hinge support 22 by a rotating shaft; the other end is connected to the upper clamp base 21 by the first push screw 23; one end of the first push screw 23 is connected to the upper clamp base 24. One end is rotatably connected to the other end, and the other end is rotatably connected to the first upper clamping frame 24; one top end of the first upper clamping frame 24 is rotatably connected to the bottom of the second upper clamping frame 26, and the other end is connected to the second push screw 25; the top of the second upper clamping frame 26 is connected to the second push screw 25; the upper clamping arrow-holding pressure plate 27 is connected to the top of the second upper clamping frame 26; the first push screw 23 extends and retracts to drive the first upper clamping frame 24 to open and close; the second push screw 25 extends and retracts to drive the second upper clamping frame 26 to open and close.

[0048] In a preferred embodiment of the present invention, the upper clamp 2 has an overall length of 2.624m, a width of 0.655m, a height of 6.1m, and a total weight of 7.005t (the screw jack weighs approximately 2.823t). It adopts a truss structure. The upper clamp 2 has clamping and opening functions. The position where the upper clamp's arrow-holding pressure plate 27 contacts the arrow body is protected with a 20mm thick wool felt pad.

[0049] In a preferred embodiment of the present invention, the center of the upper clamping arrow-holding pressure plate 27 coincides with the center of the main support bracket 6.

[0050] like Figure 8 As shown, the main support bracket 6 includes: a main arrow support 61, an arrow support base 62, and a connecting erector base 63; the main arrow support 61 is fixedly connected to the arrow support base 62 by bolts; the main arrow support 61 has an arc-shaped groove for supporting the arrow body; the arrow support base 62 is fixedly connected to the connecting erector base 63; the connecting erector base 63 is fixedly connected to the main erector structure 1. Preferably, the arrow support base 62 is welded to the connecting erector base 63, and the connecting erector base 63 is welded to the main erector structure 1. The main support bracket 6 can achieve a longitudinal adjustment range of ±25mm.

[0051] In a specific embodiment of the present invention, the main support bracket 6 is mounted on the main structure 1 of the erecting frame. During the hoisting and transfer of the entire rocket, the front end of the rocket body contacts the main support bracket 6 via hoisting, and the rear end journal rests on the lower clamp 3. The rocket body first contacts the main support bracket 6, and the lower clamp 3 is adjusted to position the rocket body. Under transportation conditions, the main support bracket 6, the auxiliary support bracket 4, and the lower clamp 3 jointly support the rocket body.

[0052] In a specific embodiment of the present invention, the lower clamp 3 is located at the tail of the erecting frame, behind the slewing shaft, and forms a two-point positioning system with the front main support bracket 6, supporting from the front and clamping from the rear. The structure of the lower clamp 3 is the same as that of the upper clamp 2, and will not be described again here.

[0053] As a specific embodiment of the present invention, the design of the connecting erecting frame base 63 is modified in conjunction with the erecting frame main structure 1 after completion, and subsequent adjustments are required based on the erecting frame structure.

[0054] As a specific embodiment of the present invention, the auxiliary arrow support 41 has an arc-shaped groove for supporting the arrow body; the inner wall of the arc-shaped groove is provided with felt.

[0055] As a specific embodiment of the present invention, the spring compression limiting structure 52 includes: an outer cylinder, a spring, and a movable column; the spring is disposed inside the outer cylinder; the movable column is movably connected inside the outer cylinder, the bottom end of the movable column abuts against the spring, and the top end of the movable column is connected to the auxiliary support bracket 4 through a pressure sensor 56 and a joint bearing 55.

[0056] As a specific embodiment of the present invention, the guide column structure 42 includes two guide column structures 42, both of which are disposed at the bottom of the auxiliary arrow support 41 and respectively disposed on both sides of the spring limiting fixture and the screw jack structure 5.

[0057] This application provides a method for operating an erection system for auxiliary support of liquid rockets, the method comprising: Step S1: The upper and lower clamps securely hold the rocket.

[0058] In step S2, the main support bracket and the auxiliary support bracket jointly support the arrow body and complete the longitudinal adjustment.

[0059] In step S3, the auxiliary support bracket automatically rises, contacts the arrow body, and presses it firmly against the arrow body.

[0060] Step S4: The rocket is transported to the launch pad, the main structure of the erector frame is docked with the launch pad, and the rocket body is erected.

[0061] In a specific embodiment of the present invention, during rocket transport, two auxiliary support brackets rise automatically and electrically, continuing to rise and press against the rocket body after contact, ensuring rocket stability. The main structure of the erector frame horizontally supports the rocket body during the entire rocket transfer process, locking and protecting it, and erects the rocket body after docking with the launch pad at the launch site. The upper clamp secures the rocket during transport, ensuring the safety of the rocket body during transport, and also secures and protects the rocket body during erection. The main support bracket and the two auxiliary support brackets support the rocket body together, enabling longitudinal adjustment to ensure rocket stability during transport. The two auxiliary support brackets employ a spring-loaded and screw-lift adjustment system, which can be manually or automatically controlled to adapt to different needs during rocket transport.

[0062] The beneficial effects achieved by this application are as follows: (1) This application adopts a three-point layout of main support bracket and two auxiliary support brackets, and iteratively optimizes the main structure of the erecting frame with zero support as the control condition to reduce the maximum deflection of the rocket body during transportation, eliminate the additional deformation caused by insufficient rigidity of the front end of the frame, and avoid the limited support force and deformation of the main structure of the erecting frame.

[0063] (2) The upper support point of the erecting cylinder in this application is connected to the erecting cylinder through an automatic connecting pin mechanism. An automatic connecting pin mechanism is also provided at the connection between the main structure of the erecting frame and the slewing shaft lug plate, which ensures that the main structure of the erecting frame and the launch pad can be quickly and accurately docked during the docking process.

[0064] (3) The main body of the erecting frame of this application is a truss structure, which integrates air conditioning pipes, venting connectors, plug-in supports, video surveillance, personnel passages, etc., thereby improving the integration of equipment and reducing additional supports.

[0065] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0066] In the description of this application, the word "for example" is used to mean "used as an example, illustration, or description." Any embodiment described as "for example" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to make and use the invention. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that the invention can be made without using these specific details. In other instances, well-known structures and processes will not be described in detail to avoid obscuring the description of the invention with unnecessary detail. Therefore, the invention is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed in this application.

[0067] The above description is merely an embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of the present invention should be included within the scope of the claims of the present invention.

Claims

1. A lifting frame system for auxiliary support of liquid rockets, characterized in that, The system includes: the main structure of the erecting frame, the upper clamp, the lower clamp, the main support bracket, the auxiliary support bracket, the spring limit fixture, and the screw jack structure; The upper clamp and the lower clamp are fixedly connected to the main structure of the erecting frame at a distance from each other; The main support bracket and the auxiliary support bracket are spaced apart and arranged on the main structure of the erecting frame; The auxiliary support bracket is connected to the main structure of the erecting frame through the spring limiting fixture and the screw jack structure.

2. The erecting frame system for auxiliary support of liquid rockets according to claim 1, characterized in that, The auxiliary support bracket includes an auxiliary arrow support and a guide column structure; The guide column structure is located at the bottom of the auxiliary arrow support.

3. The erecting frame system for auxiliary support of liquid rockets according to claim 2, characterized in that, The spring-limiting fixture and screw jack structure includes: a jack base, a spring-pressing limiting structure, a screw jack, and a servo motor; The elevator base is fixedly connected to the main structure of the erecting frame; The screw jack is fixedly connected to the jack base; One end of the spring-loaded limiting structure is fixedly connected to the screw jack, and the other end is connected to the arrow support seat through a spherical bearing; The screw jack is connected to the servo motor; A pressure sensor is also provided between the spherical bearing and the spring compression limiting structure.

4. The erecting frame system for auxiliary support of liquid rockets according to claim 2, characterized in that, The guide post structure includes: a guide post and a guide seat; The guide seat is fixedly connected to the main structure of the erecting frame; The guide post is vertically and movably connected within the guide seat.

5. The erecting frame system for auxiliary support of liquid rockets according to claim 1, characterized in that, The upper clamp includes: an upper clamp base, a hinge support, a first upper clamp holding frame, a second upper clamp holding frame, a first push screw, a second push screw, and an upper clamp arrow-holding pressure plate; The upper clamp base and the hinge support are fixedly connected to the main structure of the erecting frame. One end of the bottom of the first upper clamping frame is connected to the hinge support via a rotating shaft; the other end is connected to the upper clamping base via the first push screw. One end of the first push screw is rotatably connected to the upper clamp base, and the other end is rotatably connected to the first upper clamp holding frame; One end of the top of the first upper clamping frame is rotatably connected to the bottom of the second upper clamping frame, and the other end is connected to the second push screw; The top of the second upper clamp holder is connected to the second push screw; The upper clamp holding plate is connected to the top of the second upper clamp holding frame; The first push screw extends and retracts, causing the first upper clamp holding frame to open and close; the second push screw extends and retracts, causing the second upper clamp holding frame to open and close.

6. The erecting frame system for auxiliary support of liquid rockets according to claim 1, characterized in that, The main support bracket includes: a main arrow support bracket, an arrow support bracket base, and a connecting erecting frame base; The main arrow support is fixedly connected to the arrow support base; The main arrow support has an arc-shaped groove that supports the arrow body; The arrow support base is fixedly connected to the connecting erecting frame base; The connecting erecting frame base is fixedly connected to the main structure of the erecting frame.

7. The erecting frame system for auxiliary support of liquid rockets according to claim 2, characterized in that, The auxiliary arrow support has an arc-shaped groove that supports the arrow body; The inner wall of the arc-shaped groove is lined with felt.

8. The erecting frame system for auxiliary support of liquid rockets according to claim 3, characterized in that, The spring-compression limiting structure includes: an outer cylinder, a spring, and a movable column; The spring is disposed inside the outer cylinder; The movable column is movably connected inside the outer cylinder. The bottom end of the movable column abuts against the spring, and the top end of the movable column is connected to the auxiliary support bracket through a pressure sensor and a joint bearing.

9. The erecting frame system for auxiliary support of liquid rockets according to claim 2, characterized in that, The guide post structure includes two. Both guide column structures are located at the bottom of the auxiliary arrow support, and are respectively located on both sides of the spring limiting fixture and the screw jack structure.

10. A method for operating a lifting frame system for auxiliary support of liquid rockets, characterized in that, The method includes: The upper and lower clamps securely hold the rocket; The main support bracket and the auxiliary support bracket together support the rocket body and complete the longitudinal adjustment; The auxiliary support bracket automatically rises, contacts the arrow body, and presses it down; The rocket was transported to the launch pad, the main structure of the erector frame was docked with the launch pad, and the rocket body was erected.

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